EP3867498A1 - Structure profilee pour aeronef ou turbomachine - Google Patents
Structure profilee pour aeronef ou turbomachineInfo
- Publication number
- EP3867498A1 EP3867498A1 EP19795038.9A EP19795038A EP3867498A1 EP 3867498 A1 EP3867498 A1 EP 3867498A1 EP 19795038 A EP19795038 A EP 19795038A EP 3867498 A1 EP3867498 A1 EP 3867498A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- profiled
- length
- teeth
- clamps
- amplitude
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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- 238000011144 upstream manufacturing Methods 0.000 description 9
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- 239000000243 solution Substances 0.000 description 6
- 230000008901 benefit Effects 0.000 description 5
- 230000010354 integration Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 210000003323 beak Anatomy 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- 230000008602 contraction Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000000737 periodic effect Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000009466 transformation Effects 0.000 description 3
- 230000001154 acute effect Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 230000003252 repetitive effect Effects 0.000 description 2
- 238000000844 transformation Methods 0.000 description 2
- 210000003462 vein Anatomy 0.000 description 2
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000010363 phase shift Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/146—Aerofoil profile comprising leading edges of particular shape
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/147—Aerofoil profile comprising trailing edges of particular shape
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/14—Boundary layer controls achieving noise reductions
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/183—Two-dimensional patterned zigzag
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to the field of aeroacoustic management of aerodynamically profiled structures, or profiles of aerodynamic elements, such as for example fixed or rotating blades in a turbomachine for aircraft or in a test bench. such turbomachinery, or on a primary air inlet nozzle of the turbomachine.
- This type of fixed vane is found for example on OGV (Outlet Guide Vane) fan outlet guide vanes, or rectifiers, arranged downstream of a rotating body to straighten the air flow.
- OGV Outlet Guide Vane
- This type of rotating blade is found, for example, on a rotating blade wheel in the turbomachine, such as a fan or a non-ttled wheel.
- Ultra-High Bypass Ratio turbojet engines UHBR; configuration of faired fan motor with very high dilution rate, beyond 15
- UHBR Ultra-High Bypass Ratio turbojet engines
- IGV Inlet Guide Vanes
- the interaction of the fan's wake with IGVs, OGVs and the nozzle is one of the dominant sources of noise.
- this tightening profile extends along the leading and / or trailing edge, in other words in the direction of elongation of the structure at the leading and / or trailing edge.
- rope used in this text, it should be noted that if there is not strictly a "rope” as in the case of a beak (identified 16 below) of separation between primary and secondary flows, we will consider that the expression “in the direction of the chord (referenced 40 below) of the profile” then corresponds to the direction of what is hereinafter called “general axis (X) "Or” X axis ", namely the axis along which the fluid flow generally flows over the profiled structure concerned, this axis being typically transverse, even perpendicular, to the elongation of the profiled structure, which extends along said "direction of elongation”.
- the invention aims to provide a compromise between a reduction in noise on this structure, the aerodynamic losses to be limited there, as well as the mechanical stresses, and the integration of the profiled structure in its environment.
- the invention proposes several heterogeneous profiles with in particular the presence of tightenings over a partial extent of the line of leading edge and / or trailing edge.
- the structure has a leading edge and / or a trailing edge, at least one of which is profiled and has, in said direction of elongation, tightenings defined by successive teeth and hollows,
- this profiled structure being characterized in that, along the leading edge and / or the profiled trailing edge (s):
- the clamps have variations in amplitude (d) and / or d spacing (L2) between two peaks of successive teeth or hollows, said variations being monotonous.
- the clamps gradually connect to said smooth part of the length exposed to the air flow which is devoid thereof, and / or
- the clamps may be absent:
- the first case must make it possible to limit the possible mechanical stresses at the interfaces / junctions between a said profiled structure and a root area / attachment of a rotating blade, for example on a propeller or in between two walls of an air stream.
- the second case must make it possible to limit the tightening at the places where the turbulence is the greatest and to eliminate them elsewhere, so as not to disturb the aerodynamic behavior in these areas.
- a faired or non-ttled turbomachine with an upstream fan and having a general axis (this may be the aforementioned axis of revolution) and comprising a rotor, which can rotate around said general axis, and a stator, the stator and / or the rotor comprising profiled structures, each having all or some of the above characteristics,
- turbomachine in which the stator comprises (or the profiled structure is that of):
- annular separation wall for the separation of the air flow, downstream of the blower, between a primary flow and a secondary flow
- FIGURES - Figure 1 is a diagram in longitudinal section (axis X) of a conventional aircraft turbomachine
- - Figure 2 shows schematically the upstream area (spout) of the partition wall between the primary and secondary flows, with a solution according to the invention
- - Figure 3 can be either detail III of Figure 2, or a local diagram of profile in clamps present on what can be a helicopter blade, a fan blade, part of the rotor or rectifier, a leading edge beak or aircraft wing flap;
- FIG. 5 shows schematically an aircraft carrying structures according to the invention
- FIG. 6 to 14 schematically show various forms of tightening profiles according to the invention and which may for example correspond to zone I of Figures 1 or 5;
- FIG. 15-16 show schematically two other tightening profiles according to the invention, and in particular angularly offset (angle a);
- FIG. 17 is a local enlargement of an example of clamping zone, according to the invention, downstream of a blower;
- FIG. 18-19 show respectively an axial section of turbulence intensity in the wake of a fan of a turbofan engine, up to the OGV, and the corresponding radial evolution of the integral scale of turbulence (L) as a function of the radius (r), between the inner radius rint and the outer radius rext of the air stream, identified 20 below, and
- FIG. 20-22 schematically show parts of the length of the leading or trailing edge with clamps having variations in amplitude (d) or spacing (L2) (strictly) monotonous; in these figures, the solid lines show the real tightening profiles, the finer gray wavy lines showing phantom tightening profiles, calculated to define the mean chord and representing a reference profile from which the monotonic amplitude variations were defined and / or spacing, and
- an aircraft turbojet 10 of an aircraft 100 is shown diagrammatically and is defined as follows:
- the nacelle 12 serves as an outer casing for the various members, among which, at the front (on the left in FIG. 1) a fan 14 upstream (AM).
- AM fan 14 upstream
- the air flow (locally shown diagrammatically 38 in FIG. 4) is separated by the separating nozzle 16 from an annular wall 160 into a primary air flow and a flow of secondary air.
- the primary air flow passes through an internal annular air passage or primary stream 18 by entering the low pressure compressor 22 at the level of the inlet guide vanes 24 IGV.
- the secondary air flow is deflected by the separator nozzle 16 in an external annular air passage 20 (secondary stream) in the direction of the outlet guide vanes 26 OGV, then towards the engine outlet.
- the front part 161 of the separating spout 16 comprising the leading edge 164 located most upstream and at which the external wall 162 of the separating spout 16 joins the inner wall 163 of the separating spout 16, the upper wall 162 forming the inner ring of the secondary stream 20.
- the internal wall 163 is the radially internal wall of the spout separator 16.
- the separator spout 16 is defined by two faces: the external face of the wall 162 serving as a radially internal limit to the passage of external annular air 20 receiving the secondary flow Fs while the internal face of the wall 163 serves as a limit radially external to the internal annular air passage 18 receiving the primary flow Fp.
- the lower wall 163 of the separator spout 16 forms the outer shell of the low pressure compressor 22.
- this leading edge 164 has a profile 28 with clamps having a succession teeth 30 and hollows 32, as illustrated in the examples of FIGS. 6-17.
- structures other than on a turbomachine, such as the turbojet engine 10 may be concerned by the solution of the invention and therefore have a leading edge 164 with profile 28 with clamps having a succession of teeth 30 and hollows 32.
- FIG. 5 shows schematically an aircraft 100 on which profiled structures with such profile 28 with clamps are present, at the leading edge, on the wings 39, on a pylon 41 for supporting an engine 42 of the aircraft , on a fin 44, a stabilizer 46, a propeller or blade 48 of open-rotor, or fixed vanes 49 (stator) downstream of an open rotor or non-ttled propeller.
- there are two aircraft propulsion turbomachines comprising two groups of open-rotor, each with two rotors 480a, 480b succeeding each other coaxially, able to rotate parallel to said general axis (X), one and / or the other of these rotors comprising profiled structures 1.
- FIG. 3 diagrams locally a profile 28 in clamps present on what can be, marked 50, a helicopter blade, a blade of the fan, part of the rotor or of the stator, an edge nozzle aircraft wing or flap.
- this profile belongs to a profiled structure 1 (or aerodynamic profile), around which (from which) air flows, which is elongated in a direction Z in which the structure (or profile) has a length L1 exposed to the air flow, and
- the structure (or the profile) 1 has a leading edge 164 and / or a trailing edge 165 (the separating spout 16 does not have a trailing edge), one of which at least is profiled and therefore has, in said direction of elongation Z, clamps (profile 28) defined by said teeth 30 and hollow 32 in succession.
- the number of teeth 30 and that of the hollows 32 will be between 3 and 100, to optimize efficiency.
- clamps 28 have (see Figures 6,10,16 and 20-25, in particular):
- the amplitude d can be measured, along the X axis, between a top 300 of tooth 30 and the bottom 320, which follows in a given direction, of the hollow 32 immediately adjacent.
- FIG. 6 illustrates the advantage that there may be in that the tightenings 28 respect, transverse to the direction of elongation Z, the relation: 0.005 ⁇ d / c ⁇ 0.5, with:
- This chord c will either be the average chord over the length Li a, or that at each tightening (a tooth followed by a hollow), in said direction Z; see Figures 6.10 and 20-22.
- clamps 28 will end (at their end of connection to the smooth part) by a zone 280a which will pitch said smooth part 280 devoid of clamps; cf. figures 7-8.
- the tightening 28 at the leading edge 164 of the OGV 26 can disturb the aerodynamic properties of the OGV or make it difficult to mechanically integrate the OGV into the vein 20 (FIG. 1).
- Figures 1 1 -14 illustrate different situations of such partial areas of clamps 28 at the leading edge 164 and / or trailing 165.
- - in Figure 1 1 Clamps 28 absent at the internal end 281 of the profiles (here absent at the foot of the OGV).
- the aim is to relax the mechanical and / or aerodynamic constraints at the inner end, while maintaining good attenuation of the acoustic levels at the outer end 283 (near the outer casing 53 in the example) where the intensity of the turbulence and the scale turbulence integral or characteristic turbulence scale are important. Tightenings near the outer casing could also be useful to avoid possible separation of the boundary layer under certain regimes or flight conditions
- - in Figure 12 Clamps 28 absent at the outer end 283 of the profiles (here absent at the top of the OGV).
- the aim is to relax the mechanical and / or aerodynamic constraints at the head while maintaining good attenuation over the rest of the span of the profile or to avoid possible separation of the boundary layer at certain speeds at the foot of the structure (support , for example central hub 55 to which the annular wall 160 may belong; FIGS. 2, 4),
- Locks 28 present in the intermediate part of the profile at the level, but absent at the external end 283 and internal 281. The aim is then to eliminate the possible mechanical stresses at the junctions between the structure concerned and here the walls of the vein 20 (outer casing 53 and hub 55 in the example), by eliminating the tightening at the bottom 281 and head 283 of OGV while retaining their interest in addressing the turbulent intermediate wakes,
- Locks 28 present at the external end 283 and internal 281, but absent in the intermediate part of the profile. The aim is then to limit the introduction of tightening to the zones where the turbulence is greatest and to remove these tightening elsewhere so as not to disturb the aerodynamic behavior in these zones. In particular at a median operating speed, between idling and full speed, the separations of the boundary layer towards the external ends 283 and internal ends 281 will then be limited.
- the shape of the clamps 28 may be rounded undulations, such as sinusoidal undulations, or other shapes, such as that in fir illustrated in Figure 16.
- Figures 15, 16, but also Figure 5, the (some) clamps 28 have an acute angle ⁇ to the axis X.
- the leading edge 164 and / or the trailing edge 165 profiled extend along a line general curved having a concavity oriented upstream, as illustrated for example in Figures 6 or 10.
- the structure 1 on which we reasoned can typically, as in the non-limiting case of an application to LMOs, belong to a set of profiled structures each having all or part of the aforementioned characteristics, and the respective directions of elongation Z of which extend radially around the axis X.
- the amplitudes and / or wavelengths of the clamps 26 concerned will be greater (or therefore long) near the outer casing 53 than near the inter-vein area (hub 55 / wall 160).
- the invention makes it possible to take into account the local properties of the turbulent flow U concerned, such as that upstream of the OGVs for example, to define the geometry of the undulations as a function of the distribution. radial of the full scale of turbulence (A figure 19) in the wake of the fan 14. It is specified that the wake of figure 4 can interact as much with the OGV (above the nozzle) as with the IGV (below the spout).
- FIG. 6 shows an OGV 1/26 with undulations optimized as a function of the integral scale L of the local turbulence along the span.
- FIGS. 18 and 19 schematize respectively the intensity of turbulence and the radial evolution of the integral scale of turbulence, in the wake of the fan 14 upstream of the LMOs 26.
- the integral scale of the turbulence (L) increases suddenly, to peak just before the outside radius, rext.
- a parabolic or linear evolution as illustrated in dotted lines and dashes respectively in FIG. 19, can be used to define the monotonous evolution of tightenings.
- the clamps (28, 28a) will have, over at least part of said length (L1) exposed to the flow of air. , a geometric pattern transformed by successive scaling, via multiplicative factors, this according to the direction of elongation (L2, L2i, L2 2 , L23, ...) and / or transversely to the direction of elongation (d, di, d2, ).
- FIG. 20 if we take as the pattern reference the one in gray in the figure (boundary by dashed lines), we see that along the length L1, the length or frequency L2 of the pattern is preserved and that by against the amplitude d varies (di, d2 ). In the solution of figure 21, it is the opposite: the amplitude d is preserved and the length or frequency L2 of the pattern varies.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- General Details Of Gearings (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1859664A FR3087482B1 (fr) | 2018-10-18 | 2018-10-18 | Structure profilee pour aeronef ou turbomachine |
PCT/FR2019/052237 WO2020079335A1 (fr) | 2018-10-18 | 2019-09-24 | Structure profilee pour aeronef ou turbomachine |
Publications (2)
Publication Number | Publication Date |
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EP3867498A1 true EP3867498A1 (fr) | 2021-08-25 |
EP3867498B1 EP3867498B1 (fr) | 2023-04-19 |
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Application Number | Title | Priority Date | Filing Date |
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EP19795038.9A Active EP3867498B1 (fr) | 2018-10-18 | 2019-09-24 | Structure profilee pour aeronef ou turbomachine |
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Country | Link |
---|---|
US (1) | US11668196B2 (fr) |
EP (1) | EP3867498B1 (fr) |
JP (1) | JP7463360B2 (fr) |
CN (1) | CN113167120B (fr) |
CA (1) | CA3116259A1 (fr) |
ES (1) | ES2947820T3 (fr) |
FR (1) | FR3087482B1 (fr) |
WO (1) | WO2020079335A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2611423A (en) * | 2018-10-18 | 2023-04-05 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine for an aircraft |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201818839D0 (en) * | 2018-11-19 | 2019-01-02 | Cambridge Entpr Ltd | Foils with serrations |
AU2020205211A1 (en) * | 2019-08-02 | 2021-02-18 | Techtronic Cordless Gp | Blowers having noise reduction features |
FR3118754B1 (fr) * | 2021-01-11 | 2024-03-22 | Safran Aircraft Engines | Dispositif d’atténuation acoustique amélioré pour ensemble propulsif d’aéronef |
JP7235996B2 (ja) * | 2021-07-05 | 2023-03-09 | ダイキン工業株式会社 | 送風装置及びそれを備えた空気調和システム |
CN114563155B (zh) * | 2022-03-14 | 2023-05-19 | 中国空气动力研究与发展中心低速空气动力研究所 | 一种开式转子气动性能评估试验装置 |
FR3133646A1 (fr) * | 2022-03-16 | 2023-09-22 | Safran Aircraft Engines | Aube pour une turbomachine d’aéronef |
EP4276013A1 (fr) * | 2022-05-09 | 2023-11-15 | BAE SYSTEMS plc | Agencement et procédé de surface de commande |
WO2023218164A1 (fr) * | 2022-05-09 | 2023-11-16 | Bae Systems Plc | Agencement et procédé de surface de régulation |
WO2024010648A1 (fr) * | 2022-07-05 | 2024-01-11 | Danfoss A/S | Aubes de roue dentelées |
DE102023122281B3 (de) | 2023-08-21 | 2024-05-16 | P3X GmbH & Co. KG | Elevon mit gezahnter Hinterkante |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB789883A (en) * | 1954-08-20 | 1958-01-29 | Power Jets Res & Dev Ltd | High speed aerofoil |
JPS5115210A (en) * | 1974-07-02 | 1976-02-06 | Rotoron Inc | Zatsuongenshono fuan |
US6733240B2 (en) * | 2001-07-18 | 2004-05-11 | General Electric Company | Serrated fan blade |
US8083487B2 (en) * | 2007-07-09 | 2011-12-27 | General Electric Company | Rotary airfoils and method for fabricating same |
CN101716995A (zh) * | 2009-10-12 | 2010-06-02 | 章成谊 | 波形翼与物体的波形表面 |
US9121294B2 (en) * | 2011-12-20 | 2015-09-01 | General Electric Company | Fan blade with composite core and wavy wall trailing edge cladding |
US9249666B2 (en) * | 2011-12-22 | 2016-02-02 | General Electric Company | Airfoils for wake desensitization and method for fabricating same |
JP2016102467A (ja) | 2014-11-28 | 2016-06-02 | 株式会社デンソー | 送風装置 |
CN104612758A (zh) * | 2014-12-19 | 2015-05-13 | 中国民航大学 | 一种低损失的低压涡轮叶片 |
CN105332948B (zh) * | 2015-10-23 | 2017-08-15 | 上海交通大学 | 一种压气机仿生动叶的实现方法 |
US10539025B2 (en) * | 2016-02-10 | 2020-01-21 | General Electric Company | Airfoil assembly with leading edge element |
US10436037B2 (en) * | 2016-07-22 | 2019-10-08 | General Electric Company | Blade with parallel corrugated surfaces on inner and outer surfaces |
US10443399B2 (en) * | 2016-07-22 | 2019-10-15 | General Electric Company | Turbine vane with coupon having corrugated surface(s) |
US10858088B2 (en) * | 2016-08-31 | 2020-12-08 | David E. Shormann | Biomimetic airfoil bodies and methods of designing and making same |
FR3062432B1 (fr) * | 2017-01-30 | 2020-11-13 | Safran Aircraft Engines | Profil ameliore de bord d'attaque d'aubes |
FR3073016B1 (fr) | 2017-10-30 | 2019-10-18 | Safran Aircraft Engines | Modulation des serrations en extremite d'aube |
-
2018
- 2018-10-18 FR FR1859664A patent/FR3087482B1/fr active Active
-
2019
- 2019-09-24 US US17/286,751 patent/US11668196B2/en active Active
- 2019-09-24 CN CN201980077471.3A patent/CN113167120B/zh active Active
- 2019-09-24 WO PCT/FR2019/052237 patent/WO2020079335A1/fr unknown
- 2019-09-24 EP EP19795038.9A patent/EP3867498B1/fr active Active
- 2019-09-24 JP JP2021521301A patent/JP7463360B2/ja active Active
- 2019-09-24 CA CA3116259A patent/CA3116259A1/fr active Pending
- 2019-09-24 ES ES19795038T patent/ES2947820T3/es active Active
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2611423A (en) * | 2018-10-18 | 2023-04-05 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine for an aircraft |
GB2611423B (en) * | 2018-10-18 | 2023-08-02 | Safran Aircraft Engines | Profiled structure for an aircraft or turbomachine for an aircraft |
Also Published As
Publication number | Publication date |
---|---|
US11668196B2 (en) | 2023-06-06 |
CN113167120B (zh) | 2023-07-04 |
JP7463360B2 (ja) | 2024-04-08 |
US20210388725A1 (en) | 2021-12-16 |
ES2947820T3 (es) | 2023-08-21 |
JP2022505328A (ja) | 2022-01-14 |
FR3087482B1 (fr) | 2021-12-17 |
WO2020079335A1 (fr) | 2020-04-23 |
CN113167120A (zh) | 2021-07-23 |
EP3867498B1 (fr) | 2023-04-19 |
FR3087482A1 (fr) | 2020-04-24 |
CA3116259A1 (fr) | 2020-04-23 |
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